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An analysis method suitable for prediction of the residual strength of a stiffened composite panel containing a center crack is presented. The analysis is based on the superposition of anisotropic elasticity solutions for an infinite plate. Strength predictions are made for two panel configurations and compared with experimental data. Reasonable comparisons between predictions and data are obtained for a panel with relatively small tear straps and little crack tip damage growth prior to final failure. However, the model shows some unconservative predictions for a panel with relatively large tear straps and crack tip damage growth.
Structural engineer, Boeing Commercial Airplane Group, Seattle, WA
Professor, University of Washington, Seattle, WA
Stock #: CTR10521J